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公开(公告)号：EP1915292A1
公开(公告)日：2008-04-30
申请号：EP06791588.4
申请日：2006-08-17
发明人： MÄNZ, Christian
摘要： The present application discloses a wing box for an aircraft wing with a framework (7) and a first shell (1), wherein the framework (7) is connected to the first shell (1) such that a load acting on the first shell (1) can be transferred by the framework (7).
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公开(公告)号：EP1735211A1
公开(公告)日：2006-12-27
申请号：EP05733257.9
申请日：2005-04-18
发明人： MÄNZ, Christian
摘要： The invention relates to nose parts of the fairing of vertical and horizontal tails and wings of an aircraft with a skin and a support structure, the skin (2) being disposed on the support structure (4, 6). The support structure is provided with a plurality of ribs (6) and a plurality of stringers (4), the plurality of stringers being arranged on the plurality of ribs to support the skin. Advantageously, an improved deformation behavior can be obtained, e.g. in the event of an impact of a bird, while the weight and cost are minimized by providing the stringers.
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公开(公告)号：EP1555204A1
公开(公告)日：2005-07-20
申请号：EP05075969.5
申请日：2000-07-18
发明人： Amaoka, Kazuaki, c/o Fuji Jukogyo K.K. , Nagao, Takayuki, c/o Fuji Jukogyo K.K. , Harada, Atsushi, c/o Fuji Jukogyo K.K. , Takizawa, Naoya, c/o Fuji Jukogyo K.K. , Hideyuki, Sano, c/o Fuji Jukogyo K.K. , Toi, Yasuhiro, c/o Fuji Jukogyo K.K. , Hiraki, Megumi, c/o Fuji Jukogyo K.K.
CPC分类号： B64C3/00 , B64F5/10 , Y10T428/24174 , Y10T428/24273 , Y10T428/24289
摘要： A wing (1) of composite material has an upper skin (2), a lower skin (3) and a plurality of intermediate spars (4) arranged between the upper (2) and the lower skin (3). The intermediate spars (4) extend from roots to tips of the upper (2) and the lower skins (3). The intermediate spars (4) are integrally formed with the upper (2) and the lower skins (3) or are adhesively bonded to the upper (2) and the lower skins (3). The wing (1) has a small number of parts, needs greatly reduced time for fabrication and can be fabricated at a low cost.
摘要翻译： 复合材料的翼（1）具有布置在鞋帮（2）和下蒙皮（3）之间的上蒙皮（2），下蒙皮（3）和多个中间翼梁（4）。 中间翼梁（4）从根部延伸至鞋帮（2）和下部皮肤（3）的末端。 中间翼梁（4）与鞋帮（2）和下部蒙皮（3）整体形成或者粘合到鞋面（2）和下部蒙皮（3）。 机翼（1）具有少量部件，需要大大缩短制造时间并且可以以低成本制造。
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公开(公告)号：EP0113466B1
公开(公告)日：1988-11-30
申请号：EP83112717.0
申请日：1983-12-16
申请人： THE BOEING COMPANY
IPC分类号： B64C3/00
CPC分类号： B64C3/00
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公开(公告)号：EP0113466A1
公开(公告)日：1984-07-18
申请号：EP83112717.0
申请日：1983-12-16
申请人： THE BOEING COMPANY
IPC分类号： B64C3/00
CPC分类号： B64C3/00
摘要： A swept wing (10) for jet transports having a thickness-chord length (t/c) ratio that continuously decreases (i.e., tapers) from the wing root (14) to the wing tip (16) is disclosed. The tapered t/c ratio wing has reduced weight and improved overall efficiency when compared to conventional, constant t/c ratio wings. While the t/c ratio of the wing tapers, the combined structural and skin strength of the wing remains adequate to handle bending loads imposed by lift and engine weight. In this regard, the cross-sectional thickness of the midspan region of the wing is choosen such that the wing skin thickness can be reduced to the minimum allowable for the skin material. Also, the cross-sectional thickness of the outboard region of the wing is decreased, resulting in decreased drag and weight in this region. Further, the camber of the outboard portion of the wing is increased (as compared to the camber of a constant t/c ratio wing) to prevent the unsweeping of spanwise oriented isobars (54).
摘要翻译： 公开了一种具有连续减小的厚度弦长（t / c）比（即，从翼根（14）到翼尖（16）的锥度）的喷射输送的扫掠翼（10），锥形t / c 与传统的恒定t / c比翼相比，机翼的重量减轻，总体效率提高，虽然机翼锥度的t / c比，机翼的组合结构和表皮强度仍然足以处理由电梯施加的弯曲载荷 和发动机重量，在这方面，选择翼的中跨区域的横截面厚度，使得机翼的皮肤厚度可以减小到皮肤材料的最小允许值，而且外侧的横截面厚度 翼部的区域减小，导致该区域的阻力和重量减小，而且翼的外侧部分的外倾角增加（与恒定t / c比翼的外倾相比，以防止翼展方向的不清楚 定向等压线（54）。
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公开(公告)号：EP2799330B1
公开(公告)日：2018-06-06
申请号：EP14163491.5
申请日：2014-04-04
申请人： The Boeing Company
CPC分类号： B64D45/00 , B64C3/00 , B64C21/00 , B64C23/065 , B64C23/069 , B64D2045/009 , Y02T50/164 , Y10T156/10
摘要： The present disclosure provides a system, method, and apparatus for a protective finish for an airfoil. In one or more embodiments, the disclosed method involves providing a sheath, and applying the sheath to the surface of the airfoil. In one or more embodiments, the sheath wraps around the surface of the airfoil from the leading edge of the airfoil towards the trailing edge of the airfoil. In at least one embodiment, the sheath covers approximately 50 percent to approximately 70 percent of the chord length of the airfoil. In some embodiments, the sheath is manufactured from at least one polymer, such as a polyurethane and/or a floropolymer. In one or more embodiments, the airfoil is a winglet, a raked wing tip, and/or a wing.
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公开(公告)号：EP3213802A3
公开(公告)日：2017-11-22
申请号：EP16204424.2
申请日：2016-12-15
申请人： The Boeing Company
发明人： Podnar, Gregg W.
CPC分类号： B01D19/0052 , B01D19/0026 , B05C5/02 , B05C5/0225 , B05C17/005 , B05C17/00579 , B64C1/068 , B64C3/00 , B64D37/02 , B64F5/0009
摘要： Systems for removing gas from a sealant and transferring gas-less sealant to an applicator are provided. The system may comprise: a rotatable chamber (102) including: a first opening (104) for receiving sealant; a hollow conduit (106) arranged such that when gas accumulates in the center of the rotatable chamber when the rotatable chamber is rotating, the gas is ventable from the rotatable chamber; a second opening (108) for receiving gas-less sealant from the rotatable chamber after the gas is vented from the hollow conduit; and a motor (110) operatively configured to rotate the rotatable chamber; and a gas-less sealant applicator (112) in fluid communication with the second opening of the rotatable chamber such that gas-less sealant released by the second opening is flowable into the applicator. The system may also include a robot arm (304) including an end effector with a sealant dispensing nozzle. A method for applying sealant to an aircraft structure is also provided.
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公开(公告)号：EP2723640B1
公开(公告)日：2017-11-08
申请号：EP12716584.3
申请日：2012-04-23
发明人： DAVIES, Huw , MCKENNA, Nigel
IPC分类号： B64C23/06
CPC分类号： B64C23/069 , B64C3/00 , Y02T50/164 , Y10T29/49826
摘要： An aircraft wing assembly including: a wing having a wing box structure with an upper wing cover and a lower wing cover, and a wing tip device attached to the outboard end of the wing, the wing tip device including an upper cover and a lower cover, wherein a gap between opposing edges of the wing tip device lower cover and the lower wing cover is at least 5 mm, a seal assembly aerodynamically seals the gap, wherein the seal assembly includes a bridging component on an interior side of the gap, and a seal which fills the gap and is supported by the bridging component.
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公开(公告)号：EP2750974B1
公开(公告)日：2017-10-04
申请号：EP12753212.5
申请日：2012-08-07
发明人： TIGHE, David
CPC分类号： G01M5/0016 , B29C73/10 , B64C1/064 , B64C3/00 , B64C3/182 , B64C3/187 , B64C3/26 , B64F5/00 , B64F5/60 , Y10T29/49732 , Y10T29/49826
摘要： The present invention provides an aircraft structure comprising a structural component and a set of reinforcing straps for reinforcing the structural component, wherein the set comprises a first reinforcing strap having an inner and outer surface, wherein the inner surface is attached to a first surface of the structural component such that the first reinforcing strap extends longitudinally along the structural component and a second reinforcing strap having an inner and outer surface, wherein the inner surface is attached to the outer surface of the first reinforcing strap such that the second reinforcing strap extends longitudinally along the first reinforcing strap. The invention also provides an aircraft, a method of reinforcing an aircraft structure and a method of inspecting an aircraft structure.
摘要翻译： 本发明提供了一种飞机结构，其包括结构部件和用于加强结构部件的一组加强带，其中该组包括具有内表面和外表面的第一加强带，其中内表面附接到 使得所述第一加强带沿着所述结构部件纵向延伸，以及具有内表面和外表面的第二加强带，其中所述内表面附接到所述第一加强带的外表面，使得所述第二加强带沿着所述结构部件纵向地 第一条增强带。 本发明还提供了一种飞机，一种加强飞机结构的方法以及一种检查飞机结构的方法。
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